ES2818186T3 - High-forming multi-layer aluminum alloy package - Google Patents

Abstract

An aluminum alloy comprising 0.2 to 0.6% by weight of Fe, 0.06 to 0.25% by weight of Mn, up to 0.1% by weight of Si, up to 0.5% by weight of Cu, up to 0.25% by weight of Mg, up to 0.4% by weight of Zn, one or more additional elements selected from the group consisting of Ni up to 0.60% by weight, Ti up to 0.15% by weight, Co up to 0.60% by weight, Nb up to 0.3% by weight, Cr up to 0.25% by weight, V up to 0.2% by weight, Zr up to 0.25% by weight, Hf up to 0.3% by weight and Ta up to 0.20% by weight and up to 0.15% by weight of impurities, the remainder is Al, where the combined content of Fe, Mn, Cr, Ti, Co, Ni and V present in the alloy it ranges from 0.60% by weight to 0.90% by weight.

Description

DESCRIPTION

High-forming multi-layer aluminum alloy package

COUNTRYSIDE

In this application, high formation multi-layer aluminum alloy packages are provided.

BACKGROUND

Fine grain size is a desirable property in certain alloys because sheets made from such alloys can achieve small bending angles. Sheets that have small bending angles, in turn, can be used to prepare products that have high shaping requirements. Grain size refinement has been achieved primarily by preparing alloys containing iron (Fe) in amounts of 0.7% by weight or greater. However, the use of Fe in such high amounts results in a product with limited recyclable content. Recyclability is an important parameter for aluminum alloys. New alloys are needed that have a fine-grained structure and high recyclability.

US 2014/0322558 A1 is directed to an aluminum alloy clad material for forming comprising an aluminum alloy core material containing 3.0 to 10 Mg mass%, and the remainder is Al e unavoidable impurities, an aluminum alloy surface material that is coated on one side or both sides of the core material, the coating thickness for one side is 3 to 30% of the total thickness of the sheets, and that has a composition that includes a mass percent of 0.4 to 5.0 Mg, and the remainder is Al and unavoidable impurities, and an insert material that is interposed between the core material and the surface material, and has a temperature solidus temperature of 580 ° C or less.

Document US 2014/0193666 A1 is directed to a strip comprising an aluminum material for the production of components with high conformation requirements, where the strip comprises a central layer of an AlMgSi alloy and at least one layer of aluminum alloy outer layer arranged on one or both sides and made of a non-hardening aluminum alloy, where the at least one outer aluminum alloy layer has a lower breaking load than the central layer of an AlMgSi alloy in the T4 state, and where in state T4, the strip has a uniform elongation Ag of more than 23% transverse in the winding direction and with a thickness of 1.5 mm to 1.6 mm, a bending angle of less than 40 ° is reached in a test of transverse bending in the winding direction and the at least one outer aluminum alloy layer consists of an aluminum alloy of type AA8xxx, AA8079 or A1200,

EP 2 156945 A1 is directed to an automotive coating sheet product comprising a core layer and at least one coated layer where the core layer comprises an alloy of the following composition in% by weight: Mg 0.45-0, 8, Si 0.45-0.7, Cu 0.05-0.25, Mn 0.0-0.2, Fe up to 0.35, other elements (or impurities) <0.05 each and <0 , 15 in total, balance aluminum, and the at least one coated layer comprises an alloy of the following composition in% by weight: Mg 0.3-0.7, Si 0.3-0.7, Mn up to 0, 15, Fe up to 0.35, other elements (impurities) <0.05 each and <0.15 in total, balance aluminum.

US 2014/0356647 A1 is directed to an aluminum alloy coated material for shaping including an aluminum alloy core material containing 0.2-1.5 mass% Mg, mass% of 0.2-0.25 Si, 0.2-3.0 mass% Cu, and the remainder is Al and unavoidable impurities, an aluminum alloy surface material that is coated on one or both sides of the core material, the thickness of the coating for one of the sides is 3 to 30% of the total thickness of the sheet, and having a composition that includes a mass% of 0.2-1.5 Mg, a% of 0.2-2.0 mass of Si, Cu is restricted to 0.1 mass% or less, and the remainder is Al and unavoidable impurities, and an aluminum alloy insert material interposed between the core material and surface material, and has a solidus temperature of 590 ° C or less.

US 2010/0316887 A1 is directed to an architectural aluminum foil product in which a coated layer is applied on at least one side of the core layer. The core layer is preferably made of an alloy selected from the AA5xxx series alloys with a magnesium content greater than 3% by weight, and the clad layer (or each clad layer) is made of an alloy selected from alloys AA5005, AA5205 , AA5052, AA5252 and AA5005A. The product can be provided with an anodic film on one or both sides and the films can be covered with one or more layers, for example paint.

US 2013/0302642 A1 is directed to an aluminum foil product comprising a core layer comprising a 3xxx aluminum alloy, and a cladding layer comprising a 3xxx aluminum alloy having a Zn additive.

JP 2002-362046 A is directed to a method for manufacturing a support for a lithographic printing plate comprising the steps of obtaining the support for a lithographic printing plate by applying a surface treatment including a surface scraping process. electrochemical to aluminum alloy plate. The Cu content of the aluminum alloy plate is 0.001-1 mass% and the electrochemical surface scraping process is performed in an aqueous acidic solution containing a chemical compound that can form a Cu complex.

US 2013/0068351 A1 is directed to an aluminum alloy used in an impact extrusion process to form a metal container, where the aluminum alloy comprises at least about 97% by weight of Al, at least about 0.10 wt% Si, at least about 0.25 wt% Fe, at least about 0.05 wt% Cu, at least about 0.07 wt% Mn, and at least about 0.05 wt% weight of Mg.

RESUME

Embodiments of the invention are defined by the claims, not this summary. This summary is a high-level overview of various aspects of the invention and introduces some of the concepts that are described in more detail in the Detailed Description section below. This summary is not intended to identify key or essential characteristics of the claimed subject matter, nor is it intended to be used in isolation to limit the scope of the claimed subject matter. Subject matter is to be understood by reference to the appropriate parts of the full specification, any or all of the drawings, and each claim.

New multilayer aluminum alloy compositions are provided in this application. Multi-layer aluminum alloy compositions have high formability and oven-hardening properties. The compositions also show exceptional flexing and elongation properties. Multi-layer aluminum alloy compositions include a core layer of an aluminum-containing alloy, having a first side and a second side, and at least one cladding layer adjacent to the first side and / or second side of the core layer. .

Aluminum alloys for use as the coating layer (s) comprise about 0.2 to 0.6% by weight of Fe, 0.06 to 0.25% by weight of Mn, up to 0.1% by weight of Si , up to 0.5% Cu, up to 0.25% by weight Mg, up to 0.4% by weight Zn, one or more additional elements selected from the group consisting of Ni up to 0.60% by weight , Ti up to 0.15% by weight, Co up to 0.60% by weight, Nb up to 0.30% by weight, Cr up to 0.25% by weight, V up to 0.2% by weight, Zr up to 0, 25% by weight, Hf up to 0.30% by weight and Ta up to 0.20% by weight, and up to 0.15% by weight of impurities, the remainder is Al, where the combined content of Fe, Mn, Cr, Ti, Co, Ni and V present in the alloy ranges from 0.60% by weight to 0.90% by weight. Throughout this application, all elements are described in percent by weight (% by weight) based on the total weight of the alloy.

The one or more additional elements may comprise Ni in an amount of between about 0.01 and 0.60% by weight, Ti in an amount of between about 0.01 and 0.15% by weight, Co in an amount of between about 0.01 and 0.60% by weight, Nb in an amount of between about 0.01 and 0.3% by weight, Cr in an amount of between 0.01 and 0.2% by weight, V in a amount of between about 0.01 and 0.2% by weight, Zr in an amount of between about 0.01 and 0.25% by weight, Hf in an amount of between about 0.01 and 0.30% by weight and / or Ta in an amount of between about 0.01 and 0.20% by weight. The combined content of Fe, Mn, Cr, Ti, Co, Ni, and / or V present in the alloy ranges from about 0.60% by weight to 0.90% by weight.

Also provided in this application are multilayer metal sheets comprising a core layer and one or more skin layers. In some examples, the multilayer metal sheets described in this application comprise a core layer and a first cladding layer, where the first cladding layer comprises an aluminum alloy composition as described above. The core layer can comprise an AA6xxx alloy, an AA2xxx alloy, an AA5xxx alloy, or an AA7xxx alloy. The core layer has a first side and a second side, and the first skin layer is on the first side or the second side of the core layer. The multilayer metal sheets may further comprise a second coating layer in the center layer, where the second coating layer comprises an aluminum alloy composition as described above. In some examples, the first side of the core layer is adjacent to the first skin layer to form a first interface and the second side of the core layer is adjacent to the second skin layer to form a second interface.

The alloys described in this application can form a sheet having a grain size of 10 microns to 30 microns. In some cases, the alloys described in this application can form a sheet having a size grain from 15 microns to 25 microns.

Products prepared from multilayer metal sheets are also described in this application. A product prepared from multilayer metal sheets may include a part of the motor vehicle body, such as a body side panel, or any other product.

Other objects and advantages of the invention will become apparent from the following detailed description and non-limiting examples of the invention.

BRIEF DESCRIPTION OF THE FIGURES

Figure 1 is a graph showing the percent elongation of comparative alloys and exemplary alloys disclosed in this application. The left histogram bar for each pair is the uniform high elongation (Ag) and the right histogram bar for each pair represents the elongation at break (A80).

Figure 2 is a graph showing the internal angles after a flex test for the comparative alloys and the exemplary alloys described in this application. The left bar of the histogram for each set represents the bending angles after the alloys were subjected to a 10% elongation ("10% T preform"). The center histogram bar of each set represents the bending angles after the alloys were subjected to a 15% elongation ("15% T preform"). The right histogram bar of each set represents the bending angles after the alloys were heat treated at 180 ° C for 10 hours ("T6 aging (180 ° / 10h)").

Figure 3 is an image of a comparative alloy and an alloy disclosed in this application (not according to the invention), depicting the extent of the orange peel effect.

Figure 4 contains images of alloys and their respective grain structure images for comparative alloys and exemplary alloys described in this application.

Figure 5 shows grain structure images for comparative alloys and exemplary alloys described in this application.

Figure 6 shows grain structure images for exemplary alloys described in this application.

Figure 7 shows electron backscatter diffraction images for comparative alloys and exemplary alloys disclosed in this application.

Figure 8 shows grain structure images for a comparative alloy and for alloys described in this application (not according to the invention).

Figure 9 shows images of the grain structure for comparative multilayer sheets and for exemplary multilayer sheets described in this application. Arrows indicate coated layers on multilayer sheets.

Figure 10 shows grain structure images for a comparative multilayer sheet and for an exemplary multilayer sheet described in this application. Arrows indicate coated layers on multilayer sheets.

Figure 11 shows images of iron (Fe) particle size and distribution for comparative multilayer sheets and for exemplary multilayer sheets described in this application.

Figure 12 is a graph showing the effect of flex versus elongation (Ag [%]) for a core alloy and for an exemplary multilayer sheet described in this application.

Figure 13 is a graph showing strength level (Rp02 [MPa]) at different time intervals after solution heat treatment (SHT) for exemplary multilayer sheets described in this application.

Fig. 14 is an illustration showing the meaning of the inner bending angle (p).

Figure 15 is a graph showing the elastic limit (Rp0,2) and the tensile strength (Rm) for exemplary alloys measured at 0 ° (indicated as "L"), 45 ° and 90 ° (indicated as "T ") with respect to the rolling direction.

The first histogram bar in each set represents the yield strength measured at 0 ° in the rolling direction. The second histogram bar in each set represents the yield strength measured at 45 ° in the rolling direction. The third histogram bar in each set represents the yield strength measured at 90 ° in the rolling direction. The fourth histogram bar in each set represents the tensile strength measured at 0 ° in the rolling direction. The fifth histogram bar in each set represents the tensile strength measured at 45 ° in the rolling direction. The sixth histogram bar in each set represents the tensile strength measured at 90 ° in the rolling direction.

Figure 16 is a graph showing high uniform elongation (Ag) and elongation at break (A80) for exemplary alloys measured at 0 ° (indicated as "L"), 45 °, and 90 ° (indicated as "T" ) in the rolling direction. The first histogram bar in each set represents the high uniform elongation measured at 0 ° in the rolling direction. The second histogram bar in each set represents the high uniform elongation measured at 45 ° in the rolling direction. The third histogram bar in each set represents the high uniform elongation measured at 90 ° in the rolling direction. The fourth histogram bar in each set represents the elongation at break measured at 0 ° in the rolling direction. The fifth histogram bar in each set represents the elongation at break measured at 45 ° in the rolling direction. The sixth histogram bar in each set represents the elongation at break measured at 90 ° in the rolling direction.

Figure 17 is a graph showing the difference between elongation at break and uniform high elongation for exemplary alloys measured at 0 ° (indicated as "L"), 45 °, and 90 ° (indicated as "T") on the rolling direction. The first histogram bar in each set represents the yield strength measured at 0 ° in the rolling direction. The second histogram bar in each set represents the difference in values measured at 45 ° in the rolling direction. The third histogram bar in each set represents the difference in the measured values at 90 ° in the rolling direction. The fourth histogram bar in each set represents the difference in values measured at 90 ° in the rolling direction after subjecting the alloy to a temperature of 205 ° C for 30 minutes.

Figure 18 is a graph depicting grain size for comparative and exemplary alloys as described in this application.

Figure 19A shows a grain structure image for alloy 14 as described in this application (not according to the invention).

Figure 19B shows a grain structure image for an exemplary alloy 16 as described in this application.

Figure 20 shows images of different views of a core alloy and two exemplary multilayer alloys as described in this application after cross-die testing of the alloys. Figure 21 is a graph showing bonding results after an exposure of 0 hours (first histogram bar), 1000 hours (second histogram bar), and 3000 hours (third histogram bar) to a corrosive environment in the neutral salt spray test (NSS35 ° C) for the center of an exemplary alloy B sample as described in this application (left) compared to an exemplary center clad alloy B sample as described in this application (right) .

Figure 22A is a graph depicting the average blister size after the copper-assisted acetic acid salt spray test (CASS) for a comparative AA6014 alloy (left bar), the center of exemplary alloy sample B as described in this application (center bar) and exemplary coated center alloy sample B as described in this application (right bar).

Figure 22B is a graph depicting the percent coverage of the blister along the hatch lines of a comparative AA6014 alloy (left bar), the center of sample B of exemplary alloy as described in this application (bar center) and exemplary plated center alloy sample B as described in this application (right bar).

Figure 23A is a graph depicting the maximum filament size after filiform corrosion testing for a comparative AA6014 alloy (left bar), the center of exemplary alloy sample B as described in this application (center bar) and exemplary plated center alloy sample B as described in this application (right bar).

Figure 23B is a graph depicting the average filament size for the same for a comparative AA6014 alloy (left bar), the center of sample B of exemplary alloy as described herein. application (center bar) and exemplary alloy sample B with plated center as described in this application (right bar).

Figure 24 is a graph depicting grain size measurement for exemplary alloys as described in this application.

Figure 25A shows grain structure images for an exemplary alloy 28 as described in this application.

Figure 25B shows grain structure images for alloy 32 as described in this application (not according to the invention).

Figure 26A is a graph depicting the yield strength (Rp0.2) and the yield strength (Rm) for exemplary alloys. The left histogram bar of each set represents the elastic limit (Rp0.2). The right histogram bar of each set represents the elastic limit (Rm).

Figure 26B is a graph depicting the Rp02 / Rm ratio for exemplary alloys measured 90 ° in the rolling direction.

DETAILED DESCRIPTION

New multilayer aluminum alloy sheets are disclosed in this application which have high formability, good bake-hardening properties, and exceptional bending and elongation properties. The alloy and alloy sheets used to prepare the sheets described herein are highly recyclable.

Multilayer sheets include a core layer of an aluminum-containing alloy, having a first side and a second side, and at least one skin layer adjacent to the first side and / or second side of the core layer. The cladding layers exhibit extremely good flex and high elongation and also have a very fine grain size. Surprisingly, the coating layers as described in this application exhibit these properties despite the Fe content of up to 0.6% by weight based on the weight of the coating layer. Typically, to achieve fine grain size in a forged sheet product prepared from aluminum alloys under standard processing conditions (e.g. casting, homogenizing, hot and cold rolling, and annealing), the aluminum alloys must include 0, 7% by weight or more of Fe.

Definitions and descriptions:

The terms "invention", "the invention", "this invention" and "the present invention" used in this application are intended to refer broadly to all subject matter of this patent application and the claims that follow. It is to be understood that the statements containing these terms do not limit the subject matter described in this application nor do they limit the meaning or scope of the patent claims below.

In this description, alloys identified by AA numbers and other related designations are referred to as "series" or "6xxx". For an understanding of the number designation system most commonly used to name and identify aluminum and its alloys, see "International Alloy Designations and Chemical Composition Limits for Wrought Aluminum and Wrought Aluminum Alloys" or "Registration Record of Aluminum Association Alloy Designations and Chemical Compositions. Limits for Aluminum Alloys in the Form of Castings and Ingot ", both published by The Aluminum Association.

As used herein, the singular forms "a", "an" and "the" include the singular and plural references unless the context clearly dictates otherwise.

In the following examples, aluminum alloys are described in terms of their elemental composition in% by weight. In each alloy, the remainder is aluminum, with a maximum weight% of 0.15% for the sum of all impurities.

Multi Layer Metal Sheet

A multilayer metal sheet is provided in this application. The multilayer metal sheet includes an aluminum-containing alloy core layer having a first side and a second side and one or more cladding layers. In some examples, the core layer is coated on only one side (ie, a coating layer is present on the metal sheet). In some examples, the core layer is coated on only one side (i.e. two coating layers are present on the metal sheet).

The first side of the core layer is adjacent and contacts a first skin layer to form a first interface. In other words, no layers intervene between the first skin layer and the first side of the core layer. Optionally, the multilayer metal sheet includes a second coating layer. In these cases, the second side of the core layer is adjacent and contacts a second skin layer to form a second interface (ie, no layers intervene between the second skin layer and the second side of the core layer). The first coating layer and the second coating layer can be the same chemical composition or different chemical compositions.

Central layer

The center layer is an alloy containing aluminum. In some examples, any alloy designated as a "AA6xxx series" alloy, a "AA2xxx series" alloy, a "AA5xxx series" alloy, or a "AA7xxxx series" alloy is suitable for use as a core layer. By way of non-limiting example, AA6xxx alloys for use as a core layer may include AA6016, AA6016A, AA6013, AA6014, AA6008, AA6005, AA6005A, AA6005B, AA6005C, AA6451, AA6181A, AA6501, AA6056, AA6011, or AA6111. Exemplary non-limiting AA2xxx series alloys for use as the core layer may include AA2013 or AA2002 alloys, Exemplary non-limiting AA5xxx series alloys for use as the core layer may include AA5182, AA5754, AA5251, AlMg5 or AlMg6 alloys, Exemplary non-limiting AA7xxx series alloys for use as the core layer may include AA7075, AA7085, AA7021, AA7022, AA7049, AA7050, AA7019, AA7001, AA7003, AA7010, or AA7012 alloys,

In some examples, the alloy to use as the core layer may have the following elemental composition as provided in Table 1.

Table 1

In some examples, the alloy to use as the core layer may have the following elemental composition as provided in Table 2.

Table 2

In some examples, the core alloy described in this application also includes silicon (Si) in an amount of 1.0 % to 1.5% (for example, 1.0 to 1.4% or 1.15 to 1 , 45%) based on the total weight of the alloy. For example, the alloy may include 1.0%, 1.01%, 1.02%, 1.03%, 1.04%, 1.05%, 1.06%, 1.07%, 1.08 %, 1.09%, 1.10%, 1.11%,

1.12%, 1.13%, 1.14%, 1.15%, 1.16%, 1.17%, 1.18%, 1.19%, 1.20%, 1.21%, 1.22%, 1.23%, 1.24%, 1.25%, 1.26%, 1.27%, 1.28%, 1.29%, 1.30%, 1.31%, 1.32%, 1.33%, 1.34%, 1.35%, 1.36%, 1.37%, 1.38%, 1.39%, 1.40%, 1.41%, 1.42%, 1.43%, 1.44%, 1.45%, 1.46%, 1.47%, 1.48%, 1.49% or 1.50% of Si. All expressed in% by weight.

In some examples, the core alloy described in this application includes iron (Fe) in an amount of between 0.1% and 0.35% (for example, between 0.10% and 0.30% or between 0.12% and 0.25%) based on the total weight of the alloy. For example, the alloy may include 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18 %, 0.19%, 0.20%, 0.21%, 0.22%, 0.23%, 0.24%, 0.25%, 0.26%, 0.27%, 0.28 %, 0.29%, 0.30%, 0.31%, 0.32%, 0.33%, 0.34% or 0.35% of Fe. All expressed in% by weight.

In some examples, the core alloy described in this application also includes copper (Cu) in an amount between

0.01% and 0.20% (for example, between 0.03% and 0.18% or between 0.05% and 0.16%) based on the total weight of the alloy.

For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09 %, 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19 % or 0.20% Cu. All expressed in% by weight.

In some examples, the core alloy disclosed in this application includes manganese (Mn) in an amount between

0.01% and 0.20% (for example, between 0.02% and 0.15%, between 0.03% and 0.12%, or between 0.04% and 0.15%) based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09 %, 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19 % or 0.20% of Mn. All expressed in% by weight.

In some examples, the core alloy disclosed in this application includes magnesium (Mg) in an amount between

0.15% and 0.4% (for example, between 0.20% and 0.35% or between 0.25% and 0.35%) based on the total weight of the alloy.

For example, the alloy may include 0.15%, 0.16%, 0.17%, 0.18%, 0.19%, 0.20%, 0.21%, 0.22%, 0.23 %, 0.24%, 0.25%, 0.26%, 0.27%, 0.28%, 0.29%, 0.30%, 0.31%, 0.32%, 0.33 %, 0.34%, 0.35%, 0.36%, 0.37%, 0.38%, 0.39% or 0.40% of Mg. All expressed in% by weight.

In some examples, the core alloy described in this application includes chromium (Cr) in an amount of up to 0.1%.

(eg, 0% to 0.1%, 0.001% to 0.05%, or 0.005% to 0.04%) based on the total weight of the alloy.

For example, the alloy can include 0.001%, 0.002%, 0.003%, 0.004%, 0.005%, 0.006%, 0.007%, 0.008%, 0.009%, 0.010%, 0.011% 0.012%, 0013%, 0.014%, 0.015% , 0.016%, 0.017%, 0.018%, 0.019%, 0.020%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09% or 0.1 % of Cr. In some cases, Cr is not present in the alloy (i.e. 0%) All expressed in% by weight.

In some examples, the core alloy disclosed in this application includes nickel (Ni) in an amount up to 0.05%

(for example, 0% to 0.045%, 0.01% to 0.04%, or 0.015% to 0.034%) based on the total weight of the alloy For example, the alloy may include 0.010%, 0.011% , 0.012%, 0.013%, 0.014%, 0.015%, 0.016%, 0.017%,

0.018%, 0.019%, 0020%, 0.021%, 0.022%, 0.023%, 0.024%, 0.025%, 0.026%, 0.027%, 0.028%, 0.029%,

0.030%, 0.031%, 0.032%, 0.033%, 0.034%, 0.035%, 0.036%, 0.037%, 0.038%, 0.039%, 0.040%, 0.041%,

0.042%, 0.043%, 0.044%, 0.045%, 0.046%, 0.047%, 0.048%, 0.049% or 0.050% of Ni. In some cases, Ni is not present in the alloy (ie 0%). All expressed in% by weight.

In some examples, the core alloy described in this application may also include zinc (Zn) in an amount of up to 0.2% (eg, 0% to 0.15% or 0.05% to 0.1% ) based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09 %, 0.10%, 0.11%,

0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19%, or 0.20% of Zn. In some cases, Zn is not present in the alloy (ie 0%). All expressed in% by weight.

In some examples, the core alloy disclosed in this application includes titanium (Ti) in an amount of between 0.01% and 0.05% (for example, between 0.010% and 0.035%, between 0.012% and 0.028%, or between 0.015%). % and 0.030%) based on the total weight of the alloy. For example, the alloy may include 0.010%, 0.011%, 0.012%, 0.013%, 0.014%, 0.015%,

0.016%, 0.017%, 0.018%, 0.019%, 0.020%, 0.021%, 0.022%, 0.023%, 0.024%, 0.025%, 0.026%, 0.027%,

0.028%, 0.029%, 0.030%, 0.031%, 0.032%, 0.033%, 0.034%, 0.035%, 0.036%, 0.037%, 0.038%, 0.039%,

0.040%, 0.041%, 0.042%, 0.043%, 0.044%, 0.045%, 0.046%, 0.047%, 0.048%, 0.049% or 0.050% of Ti. All expressed in% by weight.

In some examples, the core alloy described in this application includes cobalt (Co) in an amount of up to 0.05%.

(eg 0% to 0.04% or 0.01% to 0.03%) based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, or 0.05% of Co. In some cases, Co is not present in the alloy.

(i.e. 0%). All expressed in% by weight.

In some examples, the core alloy described in this application includes niobium (Nb) in an amount up to 0.05%

(eg 0% to 0.04% or 0.01% to 0.03%) based on the total weight of the alloy. For example, the alloy can include 0.01%, 0.02%, 0.03%, 0.04%, or 0.05% of Nb. In some cases, Nb is not present in the alloy

(i.e. 0%). All expressed in% by weight.

In some examples, the core alloy described in this application includes vanadium (V) in an amount of up to 0.05%.

(eg, 0% to 0.045% or 0.01% to 0.03%) based on the total weight of the alloy. For example, the alloy may include 0.010%, 0.011%, 0.012%, 0.013%, 0.014%, 0.015%, 0.016%, 0.017%, 0.018%, 0.019%, 0.020%,

0.021%, 0.022%, 0.023%, 0.024%, 0.025%, 0.026%, 0.027%, 0.028%, 0.029%, 0.030%, 0.031%, 0.032%,

0.033%, 0.034%, 0.035%, 0.036%, 0.037%, 0.038%, 0.039%, 0.040%, 0.041%, 0.042%, 0.043%, 0.044%,

0.045%, 0.046%, 0.047%, 0.048%, 0.049% or 0.050% of V. In some cases, V is not present in the alloy

(i.e. 0%). All expressed in% by weight.

In some examples, the core alloy described in this application includes zirconium (Zr) in an amount of up to 0.05%.

(eg 0% to 0.04% or 0.01% to 0.03%) based on the total weight of the alloy. For example, the alloy can include 0.01%, 0.02%, 0.03%, 0.04%, or 0.05% of Zr. In some cases, Zr is not present in the alloy

(i.e. 0%). All expressed in% by weight.

In some examples, the core alloy described in this application includes tantalum (Ta) in an amount up to 0.05%.

(eg 0% to 0.04% or 0.01% to 0.03%) based on the total weight of the alloy. For example, the alloy can include 0.01%, 0.02%, 0.03%, 0.04%, or 0.05% of Ta. In some cases, Ta is not present in the alloy

(i.e. 0%). All expressed in% by weight.

In some examples, the core alloy described in this application includes hafnium (Hf) in an amount of up to 0.05%.

(eg 0% to 0.04% or 0.01% to 0.03%) based on the total weight of the alloy. For example, the alloy can include 0.01%, 0.02%, 0.03%, 0.04%, or 0.05% Hf. In some cases, Hf is not present in the alloy

(i.e. 0%). All expressed in% by weight.

Optionally, the core alloy compositions disclosed in this application may further include other minor elements, sometimes referred to as impurities, in amounts of 0.05% or less,

0.04% or less, 0.03% or less, 0.02% or less, or 0.01% or less. These impurities can include, without limitation,

Zr, Sn, Ga, Ca, Bi, Na, Pb or combinations thereof. Therefore, Zr, Sn, Ga, Ca, Bi, Na, or Pb can

be present in alloys in amounts of 0.05 % or less, 0.04 % or less, 0.03 % or less, 0.02 % or less, or 0.01% or less. The sum of all impurities does not exceed 0.15% (eg 0.10%). All expressed in% by weight. The remaining percentage of each alloy is aluminum.

In some examples, the alloy for use as the core layer may have the following elemental composition: 1.15 1.4% by weight of Si, 0.12-0.25% by weight of Fe, 0.05-0, 16% by weight of Cu, 0.046-0.13% by weight of Mn, 0.25-0.35% by weight of Mg, 0.016-0.06% by weight of Cr, 0-0.035% by weight of Ni, 0-0.1% by weight of Zn, 0.012-0.028% by weight of Ti, 0-0.03% by weight of Co, 0-0.03% by weight of Nb, 0-0.03% by weight of V, 0-0.03% by weight of Zr, 0.03% by weight of Ta, 0-0.03% by weight of Hf, up to 0.15% by weight of impurities and the remaining Al.

The thickness of the core layer can be from about 70% to about 90% of the multilayer metal sheets described herein. For example, in a multi-layer metal sheet with a thickness of 1000 microns, the center layer can have a thickness of from about 700 microns to about 900 microns. Facing layer ( s)

As described above, an aluminum-containing alloy for use as the clad layer (s) in multilayer metal sheets is also described. Suitable alloys for use as cladding layers include alloys containing up to 0.6% by weight Fe and one or more of the additional elements Mn, Ni, Ti, Co, Nb, Cr, V, Zr, Hf, and Ta as defined in claim 1. Alloys for use as the cladding layers exhibit extremely good flex and high elongation. These coating layer properties are achieved in part due to microstructure (eg, fine grain size), which is achieved by the specific elemental composition of the coated layer alloy. In this application an alloy is described having the following elemental composition as given in Table 3 (not according to the invention).

Table 3

This application describes another alloy having the following elemental composition as provided in Table 4 (not according to the invention).

Table 4

Another alloy is described in this application having the following elemental composition as provided in Table 5 (not according to the invention).

Table 5

Another alloy is described in this application having the following elemental composition as provided in Table 6 (not according to the invention).

Table 6

Another alloy is described in this application having the following elemental composition as provided in Table 7 (not according to the invention).

Table 7

The coated alloy described in this application includes iron (Fe) in an amount between 0.2 % and 0.6 % (for example, between 0.2% and 0.6%, between 0.2% and 0.5 %, or between 0.3% and 0.4%) based on the total weight of the alloy. For example, the alloy may include 0.15%, 0.16%, 0.17%, 0.18%, 0.19%, 0.20%, 0.21%, 0.22%, 0.23 %, 0.24%, 0.25%,

0.26%, 0.27%, 0.28%, 0.29%, 0.30%, 0.31%, 0.32%, 0.33%, 0.34%, 0.35%, 0.36%, 0.37%, 0.38%, 0.39%,

0.40%, 0.41%, 0.42%, 0.43%, 0.44%, 0.45%, 0.46%, 0.47%, 0.48%, 0.49%, 0.50%, 0.51%, 0.52%, 0.53%,

0.54%, 0.55%, 0.56%, 0.57%, 0.58%, 0.59% or 0.60% of Fe. All expressed in% by weight.

In some examples, the coated alloy described in this application also includes silicon (Si) in an amount of up to 0.1% based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%,

0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09%, 0.10%, 0.11%, 0.12%, 0.13%, or 0.14% Si. In some cases Si is not present in the alloy (ie 0%). All expressed in% by weight.

In some examples, the coated alloy described in this application also includes copper (Cu) in an amount of up to 0.5% (eg, 0% to 0.5%, 0% to 0.4%, 0.005 % to 0.45%, 0.01% to 0.4%, or 0.02% to

0.35%) based on the total weight of the alloy. For example, the alloy can include 0.001%, 0.002%, 0.003%, 0.004%, 0.005%, 0.006%, 0.007%, 0.008%, 0.009%, 0.01%, 0.02%, 0.03%, 0 , 04% or 0.05%, 0.06%, 0.07%,

0.08%, 0.09%, 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19%, 0.20%, 0.21%,

0.22%, 0.23%, 0.24%, 0.25%, 0.26%, 0.27%, 0.28%, 0.29%, 0.30%, 0.31%, 0.32%, 0.33%, 0.34%, 0.35%,

0.36%, 0.37%, 0.38%, 0.39%, 0.40%, 0.41%, 0.42%, 0.43%, 0.44%, 0.45%, 0.46%, 0.47%, 0.48%, 0.49% or

0.50% Cu. In some cases, Cu is not present in the alloy (ie 0%). All expressed in% by weight.

In some examples, the coated alloy described in this application includes magnesium (Mg) in an amount up to

0.25% (eg, 0% to 0.25%, 0.01% to 0.2%, or 0% to 0.1%) based on the total weight of the alloy.

For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09 %, 0.10%,

0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19%, 0.20%, 0.21%, 0.22%, 0.23%, 0.24%, or

0.25% Mg. In some cases, Mg is not present in the alloy (ie 0%). All expressed in% by weight.

In some examples, the coated alloy described in this application may also include zinc (Zn) in an amount of up to 0.4% (e.g., 0% to 0.4%, 0% to 0.3%, of 0.005% to 0.35%, 0.01% to 0.3%, or 0.03% to 0.3%) based on the total weight of the alloy. For example, the alloy can include 0.001%, 0.002%, 0.003%, 0.004%, 0.005%, 0.006%, 0.007%, 0.008%, 0.009%, 0.01%, 0.02%, 0.03%, 0 , 04%, or 0.05%, 0.06%, 0.07%,

0.08%, 0.09%, 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19%, 0.20%, 0.21%,

0.22%, 0.23%, 0.24%, 0.25%, 0.26%, 0.27%, 0.28%, 0.29%, 0.30%, 0.31%, 0.32%, 0.33%, 0.34%, 0.35%, 0.36%, 0.37%, 0.38%, 0.39% or 0.40% of Zn. In some cases, Zn is not present in the alloy (ie 0%).

All expressed in% by weight.

The coated alloy described in this application may further include one or more additional intermetallic promoter elements. As used in this application, the term "intermetallic activating element" refers to an element that activates the formation of intermetallic compounds, such as Al a M b, Al a M b N c, Al a M b N c O d, Al a M b N c O d

P e, o Al a Fe b M cA a lFe b M c N d, Al a Fe b M c N d O e, Al a Fe b M c N d O e P fo Al a Si b Fe c, Al a Si b Fe c M d, Al a Si b Fe c M d N e, Al a Si b Fe c M d N e O f, Al a Si b Fe c M d N e O f P g where M, N, O and P are metallic elements since b, c, d, e, f and g are integers, for example, in some cases, an integer from 1 to 100, Intermetallic activating elements (M, N, O, P) are they can select from Si, Mn, Ni, Ti, Co, Nb, Cr, V, Zr, Hf and Ta.

Optionally, the alloy includes one of these additional elements. Optionally, the alloy includes two or more of these additional elements. For example, the alloy may include a combination of Fe, Si, and one or more of Mn,

Ni, Ti, Co, Nb, Cr, V, Zr, Hf and Ta (for example, AlSixFeyMz). In another example, the alloy may include a combination of Mn and one or more of Ni, Ti, Co, Nb, Cr, V, Zr, Hf, and Ta (eg, AlMnxMy). Intermetallic promoter elements, in combination with Fe, result in an alloy with better flexural and elongation properties than, for example, AA6xxx alloys. The combination of intermetallic activating elements and

Fe also results in an alloy that has a smaller grain size than, for example, soft alloys like AA1050 and AA5005, For example, intermetallic compounds can be Al 3 Fe, Al 4 (FeMn), AlNb 2,

Al 9 Co 2 or similar.

The coated alloy disclosed in this application includes manganese (Mn) in an amount of 0.06% to 0.25% (eg 0.1% to 0.2%) based on the total weight of the alloy. For example, the alloy may include 0.06%,

0.07%, 0.08%, 0.09%, 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19%, 0.20%, 0.21%, 0.22%, 0.23%, 0.24% or 0.25% of Mn. All expressed in% by weight.

0,05 %, 0,06 %, 0 07 %, 0,08 %, 0,09 %, 0,10 %, 0,11 %, 0,12 %, 013 %, 014 %, 015 %, 016 %, 017 %, 018 %, 0,19 %, 0,20 %, 021 %, 0,22 %, 0,23 %, 0,24 %, 0,25 %, 0,26 %, 027 %, 028 %, 029 %, 030 %, 031 %, 032 %, 0,33 %, 0,34 %, 0 35 %, 0,36 %, 0,37 %, 0,38 %, 0,39 %, 0,40 %, 041 %, 042 %, 043 %, 044 %, 045 %, 046 %, 0,47 %, 0,48 %, 049 %, 0,50 %, 0,51 %, 0,52 %, 0,53 %, 0, 54 %, 0,55 % 01,56 %, 0,57 %, 0,58 %, 0,59 % o 0,60 % de Ni. En algunos casos, el Ni no está presente en la aleación (es decir, 0 %). Todo expresado en % en peso.In some examples, the coated alloy described in this application includes nickel (Ni) in an amount of up to 0.60% (eg, 0% to 0.5%, 0% to 0.4%, 0.01 0.55%, 0.02% to 0.45%, or 0.05% to 0.4%) based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04

0.05%, 0.06%, 0 07%, 0.08%, 0.09%, 0.10%, 0.11%, 0.12%, 013%, 014%, 015%, 016%, 017%, 018%, 0.19 %, 0.20%, 021%, 0.22%, 0.23%, 0.24%, 0.25%, 0.26%, 027%, 028%, 029%, 030%, 031%, 032%, 0.33%, 0.34%, 0 35%, 0.36%, 0.37%, 0.38%, 0.39%, 0.40%, 041%, 042%, 043% , 044%, 045%, 046%, 0.47%, 0.48%, 049%, 0.50%, 0.51%, 0.52%, 0.53%, 0.54%, 0, 55% 01.56%, 0.57%, 0.58%, 0.59% or 0.60% of Ni. In some cases, Ni is not present in the alloy (ie 0%). All expressed in % by weight.

In some examples, the coated alloy described in this application includes titanium (Ti) in an amount of up to 0.15% (eg, 0% to 0.12%, 0.01% to 0.15%, or 0.05% to 0.10%) based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09 %, 0.10%, 0.11%, 0.12%, 0.13%, 0.14% or 0.15% of Ti. In some cases, Ti is not present in the alloy (ie 0%). All expressed in% by weight.

In some examples, the coated alloy described in this application includes cobalt (Co) in an amount of up to 0.60% (e.g., 0% to 0.5%, 0% to 0.4%, 0, 01% to 0.55%, 0.05% to 0.45%, or 0.4% to 0.6%) based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09 %, 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19 %, 0.20%, 0.21%, 0.22%, 0.23%, 0.24%, 0.25%, 0.26%, 0.27%, 0.28%, 0.29 %, 0.30%, 0.31%, 0.32%, 0.33%, 0.34%, 0.35%, 0.36%, 0.37%, 0.38%, 0.39 %, 0.40%, 0.41%, 0.42%, 0.43%, 0.44%, 0.45%, 0.46%, 0.47%, 0.48%, 0.49 %, 0.50%, 0.51%, 0.52%, 0.53%, 0.54%, 0.55% 0.56%, 0.57%, 0.58%, 0.59% or 0.60% Co. In some cases, Co is not present in the alloy (ie 0%). All expressed in% by weight.

In some examples, the coated alloy disclosed in this application includes niobium (Nb) in an amount of up to 0.3% (eg, 0% to 0.2%, 0.01% to 0.3%, or 0.05% to 0.1%) based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09 %, 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19 %, 0.20%, 0.21%, 0.22%, 0.23%, 0.24%, 0.25%, 0.26%, 0.27%, 0.28%, 0.29 % or 0.30% of Nb. In some cases, Nb is not present in the alloy (ie 0%). All expressed in% by weight.

In some examples, the coated alloy described in this application includes chromium (Cr) in an amount of up to 0.25% (eg, 0% to 0.20%, 0% to 0.15%, 0% to 0.10%, 0% to 0.08%, 0% to 0.05%, 0.01% to 0.05%, or 0.02% to 0.04%) based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09 %, 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19 %, 0.20%, 0.21%, 0.22%, 0.23%, 0.24% or 0.25% of Cr. In some cases, Cr is not present in the alloy (i.e. 0 %). All expressed in% by weight.

In some examples, the coated alloy described in this application includes vanadium (V) in an amount of up to 0.2% (eg, 0% to 0.18%, 0.01% to 0.2%, or 0.05% to 0.15%) based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09 %, 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19 % or 0.20% V. In some cases, V is not present in the alloy (ie, 0%). All expressed in% by weight.

In some examples, the coated alloy described in this application includes zirconium (Zr) in an amount of up to 0.25% (for example, 0% to 0.20%, 0% to 0.15%, or 0 0.01% to 0.10%) based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09 %, 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19 %, 0.20%, 0.21%, 0.22%, 0.23%, 0.24% or 0.25% of Zr. In some cases, Zr is not present in the alloy (ie 0%). All expressed in% by weight. In some examples, the coated alloy described in this application includes hafnium (Hf) in an amount of up to 0.30% (eg, 0% to 0.25% or 0% to 0.20%) based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09 %, 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19 %, 0.20%, 0.21%, 0.22%, 0.23%, 0.24%, 0.25%, 0.26%, 0.27%, 0.28%, 0.29 % or 0.30% Hf. In some cases, Hf is not present in the alloy (ie 0%). All expressed in% by weight.

In some examples, the coated alloy described in this application includes tantalum (Ta) in an amount of up to 0.20% (eg, 0% to 0.15% or 0% to 0.10%) based on the total weight of the alloy. For example, the alloy may include 0.01%, 0.02%, 0.03%, 0.04%, 0.05%, 0.06%, 0.07%, 0.08%, 0.09 %, 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.18%, 0.19 % or 0.20% of Ta. In some cases, Ta is not present in the alloy (ie 0%). All expressed in% by weight.

Optionally, the coated alloy compositions disclosed in this application may further include other minor elements, sometimes referred to as impurities, in amounts of 0.05% or less, 0.04%. or less, 0.03 % or less, 0.02 % or less, or 0.01 % or less. These impurities can include, without limitation, Zr, Sn, Ga, Ca, Bi, Na, Pb, or combinations thereof. Consequently, Zr, Sn, Ga, Ca, Bi, Na, or Pb can be present in alloys in amounts of 0.05% or less, 0.04% or less, 0.03% or less, 0.02% or less or 0.01% or less. In some cases, the sum of all impurities does not exceed 0.15% (eg 0.10%). All expressed in% by weight. The remaining percentage of the alloy is aluminum.

The combined amounts of Fe, Mn, Cr, Ti, Co, Ni, and V present in the coated alloy range from 0.60% to 0.90% (for example, 0.65% to 0.85% or from 0.70% to 0.80%). For example, the combined amounts of Fe, Mn, Cr, Ti, Co, Ni, and V can be approximately 0.60%, 0.61%, 0.62%, 0.63%, 0.64%, 0 , 65%, 0.66%, 0.67%, 0.68%, 0.69%, 0.70%, 0.71%, 0.72%, 0.73%, 0.74%, 0 .75%, 0.76%, 0.77%, 0.78%, 0.79%, 0.80%, 0.81%, 0.82%, 0.83%, 0.84%, 0 , 85%, 0.86%, 0.87%, 0.88%, 0.89% or 0.90%.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.35-0.45% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0-0.05% Ni, 0-0.05% Zn, 0.10 0.12% Ti, 0-0.03% Co, 0-0.03% Nb, 0-0.03% V, 0-0.03% Zr, 0-0.03% Ta, 0-0.03 % Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.35-0.45% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0-0.05% Ni, 0-0.05% Zn, 0.10 0.12% Ti, 0-0.03% Co, 0-0.03% Nb, 0.12-0.18% V, 0-0.03% Zr, 0-0.03% Ta, 0-0 , 03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.2-0.3% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0.2-0.3% Ni, 0-0.05% Zn, 0-0.05% Ti 0-0.03% Co, 0-0.03% Nb, 0-0.03% V, 0-0.03% Zr, 0-0.03% Ta, 0-0, 03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.35-0.45% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0.2-0.3% Ni, 0-0.05% Zn, 0-0.05% Ti 0-0.03% Co, 0.05-0.2% Nb, 0-0.03% V, 0-0.03% Zr, 0-0.03% Ta, 0- 0.03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.2-0.3% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0.2-0.3% Ni, 0-0.05% Zn, 0-0.05% Ti 0.2-0.3% Co, 0-0.03% Nb, 0-0.03% V, 0-0.03% Zr, 0-0.03% Ta, 0- 0.03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.2-0.3% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0.4-0.6% Ni, 0-0.05% Zn, 0-0.05% Ti 0-0.03% Co, 0-0.03% Nb, 0-0.03% V, 0-0.03% Zr, 0-0.03% Ta, 0-0, 03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.2-0.3% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0-0.03% Ni, 0-0.05% Zn, 0-0.05% Ti, 0 , 4-0.6% Co, 0-0.03% Nb, 0-0.03% V, 0-0.03% Zr, 0-0.03% Ta, 0-0, 03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.15-0.25% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0-0.05% Ni, 0-0.05% Zn, 0-0.05% Ti, 0 , 2-0.3% Co, 0-0.03% Nb, 0-0.03% V, 0-0.03% Zr, 0-0.03% Ta, 0-0, 03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.4-0.55% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0.1-0.2% Ni, 0-0.05% Zn, 0-0.05% Ti 0.1-0.2% Co, 0-0.03% Nb, 0-0.03% V, 0-0.03% Zr, 0-0.03% Ta, 0- 0.03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.4-0.55% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0-0.05% Ni, 0-0.05% Zn, 0-0.05% Ti, 0 , 2-0.3% Co, 0-0.03% Nb, 0-0.03% V, 0-0.03% Zr, 0-0.03% Ta, 0-0, 03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1 % Si, 0.4-0.55 % Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0.2-0.3% Ni, 0-0.05% Zn, 0-0.05% Ti 0-0.05% Co, 0-0.03% Nb, 0-0.03% V, 0-0.03% Zr, 0-0.03% Ta, 0-0, 03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.4-0.55% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0.05-0.15% Ni, 0-0.05% Zn, 0.05% Ti, 0-0.05% Co, 0-0.03% Nb, 0-0.03% V, 0-0.03% Zr, 0-0.03% Ta, 0-0.03 % Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.4-0.55% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0-0.15% Ni, 0-0.05% Zn, 0-0.05% Ti, 0 -0.05% Co, 0-0.03% Nb, 0-0.03% V, 0.2-0.3% Zr, 0-0.03% Ta, 0-0, 03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.35-0.45% Fe, 0-0.05% Cu, 0.15-0.25 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0-0.05% Ni, 0-0.05% Zn, 0.1 0.12% Ti, 0-0.03% Co, 0-0.03% Nb, 0-0.03% V, 0-0.03% Zr, 0-0.03% Ta, 0-0.03 % Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.4-0.55% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0-0.05% Ni, 0-0.05% Zn, 0.1 0.15% Ti, 0-0.03% Co, 0-0.03% Nb, 0.02-0.1% V, 0-0.03% Zr, 0-0.03% Ta, 0-0 , 03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.4-0.55% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0-0.05% Ni, 0-0.05% Zn, 0.02 0.08% Ti, 0-0.03% Co, 0-0.03% Nb, 0.12-0.18% V, 0-0.03% Zr, 0-0.03% Ta, 0-0 , 03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.4-0.55% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0-0.05% Ni, 0-0.05% Zn, 0.1 0.15% Ti, 0-0.03% Co, 0-0.03% Nb, 0-0.05% V, 0-0.03% Zr, 0.05-0.15% Ta, 0-0 , 03% Hf, up to 0.15% impurities and the remaining Al.

In some examples, the coated alloy may have the following elemental composition: 0-0.1% Si, 0.4-0.55% Fe, 0-0.05% Cu, 0.11-0.17 % Mn, 0-0.1% Mg, 0-0.05% Cr, 0-0.05% Ni, 0-0.05% Zn, 0.1 0.15% Ti, 0-0.03% Co, 0-0.03% Nb, 0-0.05% V, 0-0.03% Zr, 0-0.03% Ta, 0.15-0 , 25% Hf, up to 0.15% impurities and the remaining Al.

As described above, multilayer metal sheets can contain one coating layer or more than one coating layer. In some cases, multilayer metal sheets contain only a first coating layer. In some cases, multilayer metal sheets contain a first coating layer and a second coating layer. In some cases, the first coating layer and the second coating layer are identical in composition. In some cases, the first coating layer and the second coating layer differ in composition.

The thickness of the first coating layer and the second coating layer can be from about 2.5% to about 20% of the total thickness of the sheet. For example, the first and second coating layers can each be about 20%, 19.5%, 19%, 18.5%, 18%, 17.5%, 17%, 16.5%, 16%. , 15.5%, 15%, 14.5%, 14%, 13.5%, 13%, 12.5%, 12%, 11.5%, 11%, 10.5%, 10%, 9.5 %, 9%, 8.5%, 8%, 7.5%, 7%, 6.5%, 6%, 5.5%, 5%, 4.5%, 4%, 3.5%, 3%, or 2.5% of the total thickness of the sheet. The first coating layer and the second coating layer can have the same thickness as each other, although it is not necessary. Elaboration procedures

Multi-layer metal foils, as described in this application, include a core layer, a first coating layer, and optionally a second coating layer and can be made using any conventional method known to those skilled in the art. . A coated layer as described in this application can be coupled to a core layer as described in this application through any means known to one of ordinary skill in the art. For example, a coated layer can be coupled to a core layer by direct cooling co-casting as described, for example, in US Patent Nos.

7,748,434 and 8,927,113; by hot and cold rolling of a composite molten ingot as described in US Pat. 7,472,740; or by roll bonding to achieve the required metallurgical bond between core and liner. Optionally, the multilayer metal sheet can be made by hot metal rolling or the like to join the liner and the core.

Optionally, the alloys described in this application for use as the core and the cladding layers can be cast using any suitable casting method known to those skilled in the art. As some non-limiting examples, the casting process can include a direct cooling (DC) casting process and a continuous casting (CC) process. The casting process can be performed according to the standards commonly used in the aluminum industry, as known to a person skilled in the art. The QC process may include, but is not limited to, the use of dual belt casters, dual roll casters, or block casters.

In some examples, the casting process is performed using a DC casting process to form a cast ingot. The molten ingot can be subjected to other processing steps. In some examples, the processing steps include subjecting the metal ingot to a homogenization step, a hot rolling step, a cold rolling step, and / or an annealing step, as is well known to those skilled in the art. matter.

In the homogenization step, an ingot prepared from the alloy compositions described in this application is heated to a temperature ranging from about 500 ° C to about 580 ° C. The ingot is allowed to soak (that is, it is held at the indicated temperature) for a period of time. In some examples, the ingot is allowed to soak for up to 48 hours.

After the homogenization step, a hot rolling step can be performed. Before the start of hot rolling, the homogenized ingot can be allowed to cool to about 480 ° C. Ingots can be hot rolled to gauge 4mm to 16mm thick. The hot rolling temperature can range from about 200 ° C to 450 ° C.

Optionally, a cold rolling step can be carried out to obtain an intermediate gauge. The rolled gauge can then be subjected to an annealing process at a temperature of about 250 ° C to about 450 ° C, with a soak time of about 2 hours and controlled cooling to room temperature (for example, about 20 ° C to about 25 ° C). including 20 ° C, 21 ° C, 22 ° C, 23 ° C, 24 ° C or 25 ° C) at a rate of approximately 5 ° C / hour up to 200 ° C / hour. After the annealing procedure, the rolled gauge can be cold rolled to a final gauge thickness of approximately 0.7mm to 2.2mm. Cold rolling can be performed to result in a final gauge thickness that represents an overall gauge reduction of 20% to 95%. Subsequently, the multilayer package can be subjected to a solution heat treatment step at a temperature of about 500 ° C to 580 ° C, with air or water quenching.

After the solution heat treatment step, the multilayer package can optionally be subjected to a pre-aging treatment by heating it to a temperature of about 40 ° C to 140 ° C for a period of time of about 30 minutes to 8 hours. For example, pre-aging treatment can be carried out at a temperature of 40 ° C, 50 ° C, 60 ° C, 70 ° C, 80 ° C, 90 ° C, 100 ° C, 110 ° C, 120 ° C , 130 ° C or 140 ° C. Optionally, the pre-aging treatment can be performed for 30 minutes, 1 hour, 2 hours, 3 hours, 4 hours, 5 hours, 6 hours, 7 hours or 8 hours.

Properties of multilayer metal sheets and alloys

Multi-layer metal foils and alloys, as described in this application, have high formability and exhibit exceptional bending and elongation capabilities. The alloys show an elongation at break (A80) of at least 20% (for example, at least 25%, at least 30%, or at least 35%) and a uniform elongation (As) of at least 18% (for example, at least 20% or at least 27%). Alloys and sheets are also highly recyclable.

The alloys described in this application, particularly the alloys for use as cladding layers, can achieve very low bending angles. For example, the alloys described in this application can achieve bending angles of less than 9 ° after being subjected to uniaxial preforming at 15% at 90 ° in the rolling direction and / or aging at 180 ° C for up to 10 hours depending on methods known to those skilled in the art.

The alloys described herein, particularly the alloys for use as cladding layers, can be used to produce a sheet having a fine grain size. As used in this application, a size of Fine grain refers to a grain size within the range of about 10 microns to about 30 microns.

Alloys for use as cladding layers simultaneously show fine grain size along with high elongation at break (A80) in the longitudinal, transverse and diagonal directions in the rolling direction. In these examples, the combined content of Fe, Mn, Cr, Ti, Co, Ni, and / or V present in the alloy can range from 0.60% by weight to 0.90% by weight (for example, from 0 , 65% by weight to 0.85% by weight or 0.70% by weight to 0.80% by weight).

Procedures for use

The aluminum alloys and multilayer metal sheets described in this application can be used in transportation applications, including automotive, aeronautical, and railway applications. In some cases, alloys and foils can be used to prepare motor vehicle body part products, such as a body side panel, an outer door panel, an outer trunk lid panel, or a hood. Exterior. Multi-layer metal sheet can also be used to produce deep drawn interior door panels, complicated interior trunk lid panels, as well as highly deformed structural interior panels and tunnels. The aluminum alloys and multilayer metal sheets described in this application can also be used in aircraft or rail vehicle applications, to prepare, for example, external (eg, exterior cladding panels) and internal panels.

The following examples will serve to further illustrate the present invention without, at the same time, constituting any limitation thereof. Rather, various embodiments, modifications, and equivalents thereof may be resorted to which, after reading the description in this application, may be suggested to those skilled in the art without departing from the spirit of the invention. During the studies described in the following examples, standard procedures were followed, unless otherwise indicated. Some of the procedures are described below for illustrative purposes.

EXAMPLE 1

The alloys for use as the cladding layers as described in this application were prepared by casting the ingot alloys in molds, homogenizing the ingots at 540 ° C for 10 hours, hot rolling the homogenized ingots at 340 ° C - 370 ° C , and then allowing the hot rolled sheets to cool to room temperature. Subsequently, the sheets were cold rolled to 1 mm and annealed at a maximum metal temperature of 540 ° C for 70 seconds.

The elemental composition ranges for the alloys prepared are shown in Table 8. Comparative Alloy 1 is an AA8079 alloy containing primarily aluminum and iron. Comparative Alloy 2 is AA1050 Alloy, Comparative Alloy 3 is AA5005 Alloy, Alloys 1, 2, 3, 4, 5, 6, 7, 8 and 9 are exemplary alloys disclosed in this application.

Table 8

All expressed in % by weight. Up to 0.15 % by weight impurities. The rest is Al.

* not according to the invention

Elongation and bending

The elongation and flexural properties of the exemplary and comparative alloys were measured. The elongation was measured according to the DIN EN ISO 6892-1: 2009 method, at 90 ° in the rolling direction. The internal bending angle (p) was measured after uniaxial preforming of the sample 10% or 15% transverse in the rolling direction or after artificial aging at 180 ° C for 10 hours. An illustration representing the meaning of the internal bending angle (p) is provided in Figure 14. The bending test was carried out according to the DIN EN ISO 7438 procedure; the bending line was parallel in the rolling direction, the distance between the two rollers before bending was twice the thickness of the bent metal, and the punch radius was 0.2mm with a punch angle of 3 °.

As shown in Figure 1, alloys 1,2, 3, 4 and 7 showed relatively high percentages of uniform elongation (Ag) and elongation at break (A 80). Alloys 8 and 9, containing Ti and Mn, showed improved Ag and A80 values over AA5005 alloy represented as Comparative 3 alloy, which does not include Ti or Mn. Comparative Alloy 3 also includes more Mg than Alloys 8 and 9,

All the exemplary alloys showed very good bending properties compared to the comparative alloys. Figure 2 shows the bending angles after the alloys were subjected to a 15% elongation ("15% T preform" in Figure 2), a 10% elongation ("10% T preform" in Figure 2 ), and then heat treatment at 180 ° C for 10 hours ("T6 aging (180 ° / 10 h)" in Figure 2).

The alloys were also tested for the degree of formation deformation, such as orange peel defects. As shown in Figure 3, Alloy 8 showed no orange peel effects, while Comparative Alloy 2 exhibited severe orange peel defects.

Grain structure

The grain structures for the comparative alloys and the exemplary alloys described in this application were analyzed by light microscopy using a scanning electron microscope backscattered electron diffraction (SEM-EBSD) technique. For the light microscopy method, the samples were prepared following standard metallographic procedures known to those of skill in the art. The samples were anodized using Barker's reagent at a voltage of 30 V for 2 minutes. To prepare a 1000 ml solution of Barker's reagent, 60 ml of tetrafluoroboric acid solution (32%) was mixed with 940 ml of water. The grain structure was observed under polarized light using a Leica DM6000 microscope (Leica Microsystems Inc .; Buffalo Grove, IL). Figure 4 contains alloy images and their respective grain structure images for comparative alloys and exemplary alloys. Figures 5 and 6 show that increasing the weight percentages Fe, Ni, Co and Nb reduces the grain size. Also, Alloy 4 (see Figure 5), which contains 0.4% Fe, 0.1% Ti, 0.1% V, and 0.1% Mn, exhibits fine grain size. Figure 6 shows that Alloy 6, which includes Co, and Alloy 5, which includes Ni, have a very fine grain size. Both alloys 4 and 5 have a very low Fe content.

Electron backscatter diffraction (EBSD) was performed on a field emission scanning electron microscope (Zeiss SUPRA-40; Carl Zeiss Microscopy CmbH; Jena, Germany) and analyzed using an Oxford-Canal data analyzer 5, A threshold level for grain boundaries was established as 10 ° disorientation. The EBSD images are shown in Figure 7 for Comparative Alloy 2 (labeled "Ref. AA1050"), Comparative Alloy 1 (labeled "Ref. AA8079"), Alloy 6, Alloy 2, Alloy 3, and Alloy 4, The grain size was measured for the EBSD alloys and the data is provided in Table 9, where Dx is the average grain diameter parallel to the x-axis and Dy is the average grain diameter parallel to the y-axis.

Table 9

* not according to the invention

The effect of the texture on the types of alloy was analyzed. There was no significant effect on alloy properties, such as elongation and flex, as a result of variations in texture.

The grain structure was also analyzed for Comparative Alloy 3 ("Ref. AA5005"), Alloy 7, Alloy 8, and Alloy 9 (see Figure 8). There was no significant grain reduction for alloys 7 and 8, which contain 0.2% by weight of Fe, compared to a comparative alloy 3. However, the addition of 0.45% by weight of Fe, 0, 14 wt% Mn, and 0.1 wt% Ti produces a fine grain size (alloy 9).

In synthesis, the data shows that very good bending and fine grain size performance comes from including Fe at a level of 0.4% by weight, as shown in alloys 4 and 9. In addition, the addition of Co , Ni, and / or Nb similarly leads to good bending performance and fine grain size comes from lower Fe levels (eg 0.25 wt%), as shown in Alloy 2.

EXAMPLE 2

The multilayer metal sheets were prepared by melting an ingot that was double coated onto an AA6016 core, homogenizing the ingot at 545 ° C / -5 ° C for at least four hours, and hot rolling the ingot to a thickness of 10 mm at a temperature suitable for automatic annealing (approximately 430 ° C). The hot rolled sheets were then cold rolled to a thickness of 1.02 mm, and then the solution was heat treated at a peak metal temperature ranging from 545 ° C to 565 ° C. Optionally, an interconnection step was performed at 4 mm at a temperature of 350 ° C for 2 hours (see table 10).

As shown in Table 10, Alloy AA6016 was used as the core for Sample A and Alloy 12 was used as the coating for Sample A. See Table 11 for Alloy 12, Alloy 12 contains 0.4% in weight of Fe, 0.14% by weight of Mn, and 0.1% by weight of Ti. Alloy AA6016 was also used as the core for Sample B and Alloy 13 was used as the coating layers for Sample B. See Table 11 for Alloy 13, Alloy 13 is similar to Alloy 12 except that Alloy 13 additionally includes 0.15% by weight of V. Comparative samples A and B each include AA6016 alloy as the center and 11% of Comparative Alloy 4 as the cladding layers. Comparative Sample C includes AA6016 as the core and AA5005 alloy as the cladding layers.

Table 10

Table 11

All expressed in % by weight. Up to 0.15 % by weight impurities. The rest is Al.

Recyclability

For recycling purposes, the Fe content of the multilayer sheet should be 0.28% or less to avoid 6xxx scrap containing Fe. Fe levels higher than 0.28% in a 6xxx alloy (for example, AA6016 alloy or AA6014 alloy) have detrimental effects on elongation and flexure. The elemental content of a multilayer sheet as described in this application (sample C), which contains 0.45% by weight of Fe in the coated layers, and of a comparative multilayer sheet (comparative sample D), which contains 1.1% Fe in the coated layers, shown in Tables 12 and 13, respectively. As shown in Table 12, the iron content of the multilayer sheets as described in this application was 0.25%, which is within the acceptable limit in terms of recyclability. The iron content of the comparative multilayer sheet, prepared using an AA8079 coating, was 0.38%, indicating that the comparative multilayer sheet is not suitable for recycling (see Table 13).

Table 12

Table 13

Grain structure

As described above, a fine grain size is needed to draw parts that demand high conformation and also to avoid the effects of orange peel. The grain structure was analyzed for each of the samples A and B and the comparative samples A and B. As shown in figure 9, the grain size in the samples A and B, which contained 0.45% by weight Fe in the coating layer is relatively small and similar in size to Comparative Sample B, which contained 1% by weight of Fe in the coating layer. The grain sizes of samples A and B are smaller than comparative sample A, which was processed using an interconnection step, as described above. The grain size in sample A was also compared to comparative sample C. As shown in Figure 10, the grain size in sample A is finer than in comparative sample C.

Particle size distribution ( pm)

The Fe particle distribution was analyzed for each of Samples A and B and Comparative Samples A and B. As shown in Figure 11, the particle size of Fe in Samples A and B is small. Comparative samples A and B, which have a high Fe content, have more Fe particles than samples A and B. As samples A and B have a similar or smaller grain size compared to comparative samples A and B , the fine grain size of samples A and B results from the fine particle size of Fe and also from the effect of intermetallic promoter elements, such as Mn, Ni, Ti, Co, Nb, Cr, Zr, Hf, Ta and V.

Elongation and flexing of the multilayer package compared to a monolithic core alloy High elongation and very good flex are key criteria for parts that require high conformation, such as motor vehicle parts (e.g. bodywork, inner panels of the door, trunk lid inner panels, trunk lid outer panels, hood inner panels, front wall parts), etc.) Sample A, as described above, and the monolithic center alloy of the sample A underwent 15% preform. The elongation and internal bending angle were compared for the monolithic core alloy of sample A and for sample A. High elongation was achieved with both the monolithic core alloy and the multilayer package as described in this application by the use of different stages of heat treatment solution. See Figure 12, However, Sample A showed superior flex compared to the alloy in the center of Sample A. Specifically, Sample A (i.e. a multilayer package) maintained very good flex at an angle. internal bending less than 15 ° and an elongation (Ag) of 90 ° in the rolling direction of more than 23%.

Endurance

For automotive deep drawn parts, a lower incoming resistance is required to minimize springback effects. According to industry standards, the incoming resistance is guaranteed to be within a certain range for up to 6 months after solution heat treatment. Therefore, suitable parts must demonstrate stability in strength properties over a period of time by maintaining strength values between 70 MPa and 110 MPa. Strength levels for samples A and B were measured on different days after solution heat treatment (SHT) according to DIN EN ISO 6892-1: 2009 and 90 ° in the rolling direction. Strength levels of multilayer packages as described in this application, such as samples A and B described above, remained within the range of 70 MPa to 110 MPa for up to 180 days. See figure 13,

Paint Bake Response

Minimum paint bake response for multilayer packages Samples A and B were determined after 2% preforming at 90 ° in the rolling direction and artificial aging of 185 ° C for 20 minutes. The elastic limit, determined as the Rp0.2 value, was greater than 160 MPa. The maximum elastic limit, determined as the value of Rm, was greater than 220 MPa. The total elongation, determined as the As0 value, was greater than 18%.

Cross matrix

Cross die tests were performed on the center of sample A and on samples A and B. See Table 10. Cross die tests were performed with a standard cross die tool at a stamping force of 25 kN, a stamping speed of 20 mm / min, and a stamping depth of between 40-60 mm. The size of the initial blanks was 250mm wide and 250mm long and the initial thickness was 1.02mm. The sheets were lubricated using an electrostatic spray bar with a hot casting at a coating weight of 1.5 g / m2 to eliminate possible friction effects during the cross die test. As shown in figure 20, samples A and B performed better in the cross-die stamping test than the comparative center of sample A. Specifically, sample A provided a depth of 58 mm and sample B provided a depth of 55 mm, while the comparative center of sample A provided a depth of only 45 mm.

Corrosion and bonding

For automotive panels, the alloys formed from the ingots must be resistant to corrosion tests. Automotive corrosion such as Copper Accelerated Acetic Acid Salt Spray (CASS) and filiform tests. The CASS test exposes samples to a highly corrosive environment for corrosion resistance analysis. The filiform test is used to analyze the corrosion of coated alloy samples. Another important criterion may be the bonding performance of the exemplary coating surface.

The center of sample B and the central coated sample B were analyzed for comparison. Figure 21 shows the results of analyzing the bonding performance of the different alloys. A neutral salt spray test (NSS 35 ° C) was used to evaluate the bonding performance of the alloys. The NSS 35 ° C test was performed according to specifications known to those skilled in the art and consistent with the following: The bonding adhesive used for the NSS 35 ° C test was BeTAMATE ™ BM1630 (Dow Automotive Systems). Bound samples were Zn phosphated and E coated prior to NSS testing at 35 ° C. Loss of strength was measured according to the test standard DIN EN 1465, Sample B, as well as the center of sample B, showed good bonding results, even after 3000 hours exposure to a corrosive environment defined in the standard DIN EN ISO 9227, The maximum allowable strength loss of 20% was not observed for any of the alloys. Figures 22A and 22B show the results of surface analysis of sample B, the center of sample B, and a comparative alloy, AA6014, after CASs tests. The CASS test was carried out according to DIN EN ISO 9227, Before exposure to corrosive conditions, the samples were phosphated with Zn and coated with E according to specifications known to those skilled in the art, and then prepared with scratches according to DIN EN ISO 17872. Figure 22A shows that the average blister in the coating measured on corroded scratches was less than 1 mm. Figure 22B shows the coverage of the blisters in the coating along the scratches. Figure ^22b shows that both alloys, sample B and the center of sample B, demonstrated superior resistance to blistering than the comparative AA6014 alloy,

Figures 23A and 23B show the results of surface analysis of sample B, the center of sample B, and the comparative alloy, AA6014, after filiform testing. The samples were phosphated with Zn and coated with E. The samples were analyzed under filiform corrosion conditions according to DIN EN ISO 9227, The filament sizes were measured according to DIN EN ISO4628-10, Both sample B and the center of sample B performed as well or better than the AA6014 comparative alloy,

In both CASS and filiform corrosion tests, the exemplary alloys described in this application demonstrated superior corrosion resistance compared to the comparative AA6014 alloy,

Resume

High build parts such as motor vehicle parts (eg body sides) require maximum elongation, superior flex properties, fine grain size and must be highly recyclable. As described above and summarized in Table 14 below, sample A and B multilayer packages are capable of meeting each of these requirements. Multilayer comparative sheets, containing coating layers prepared from AA1050, AA8079 or AA5005 alloys, suffered in one or more of the required areas.

Table 14

EXAMPLE 3

The alloys for use as cladding layers as described in this application were prepared as described above in Example 1. The elemental composition ranges for the alloys prepared are shown in Table 15. Comparative Alloy 5 is an alloy containing mainly aluminum, silicon and iron. Comparative Alloy 6 is an alloy that contains primarily aluminum, silicon, iron, and manganese. Alloys 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, and 24 are prototypical alloys.

Table 15

All expressed in % by weight. Up to 0.15 % by weight impurities. The rest is Al.

* not according to the invention

Strength and elongation

The strength and elongation properties of the alloys listed in table 15 were measured in the T4 temper, See examples 15 and 16, The yield strength and the tensile strength were measured according to the DIN EN ISO 6892-1 method: 2009, at 0 ° (longitudinal), 45 ° and 90 ° (transverse) in the rolling direction. Elongation was measured according to the DIN ^e N ISO 6892-1: 2009 method, at 0 °, 45 ° and 90 ° in the rolling direction.

As shown in Figure 15, alloys 14-24, which contained Fe in the range of 0.2 to 0.45% by weight, exhibited elastic limits (Rp0.2) and tensile strength (Rm) similar to that alloys containing higher amounts of Fe (ie Comparative Examples 5 and 6). As shown in Figure 16, alloys 14-24 exhibited relatively high uniform elongation (Ag) and elongation at break (A80) percentages in all measured directions. In addition, alloys containing 0.45 wt% or 0.48 wt% Fe in combination with Mn, Ti, and V (i.e., alloys 22, 23, and 24) produced high elongation at the values of break (A80) in all three directions and, in particular, at 0 ° in the rolling direction. Figure 17 shows the difference between the percentages of elongation at break and uniform elongation for Comparative Alloy 5, Comparative Alloy 6, and Alloys 14-24 at 0 °, 45 °, and 90 ° in the rolling direction. The elongation properties of the alloys were also measured in the T62 temper in the transverse direction. T62 tempering was achieved by heating the alloy for 30 minutes at 205 ° C. As shown in Figure 17, alloys containing Ti and V (ie, alloys 22, 23, and 24) resulted in high A80 values in the cross direction. Grain size

The grain size for the comparative alloys and exemplary alloys was analyzed by light microscopy using a backscattered electron diffraction technique on a scanning electron microscope (SEM-EBSD). As shown in Figure 18, alloys 14 and 15 containing iron and aluminum only or iron, manganese and aluminum only resulted in relatively large grain sizes. However, alloys 16 and 19-24 all show grain size values of 25 µm and less. Alloys 17 and 18 showed a grain size between 25 pm and 30 pm. SEM images of Alloy 14 and Alloy 16 are shown and compared in Figures 19A and 19B.

Resume

In some cases, optimal formability was observed in alloys with the smallest average grain size, greatest elongation (A80) at 0 ° (indicated as "L"), 45 °, and 90 ° (indicated as "T") in the rolling direction and the combined composition of Fe, Mn, Cr, Ti, Co, Ni and V was between 0.60 and 0.90% by weight (eg, 0.60% by weight <[Fe Mn Cr Ti Co Ni V] <0.90% by weight).

EXAMPLE 4

The alloys for use as cladding layers as described in this application were prepared as described above in Example 1. The elemental composition ranges for the alloys prepared are shown in Table 16, Alloys 25, 26, 27, 28 , 29, 30, 31, 32, 33, 34 and 35 are exemplary alloys. To increase the recycle content of the smelting alloy with scrap coming from the 2xxx, 5xxx, 6xxx and 7xxx alloys of the core alloy, some additions of Si, Cu, Mg and Zn were tested in the cladding layer. .

Table 16

All expressed in% by weight. Up to 0.15% by weight impurities. The rest is Al.

* not according to the invention

Grain size

As shown in Figure 24, increasing the amount of Si, Cu, Mg, and Zn in the coated alloy can affect the grain size. The smallest average grain size for exemplary alloys 25 through 33 was observed in Alloy 28 (Figure 25A) and the largest average grain size was observed in Alloy 32 (Figure 25B). Alloys 34 and 35 demonstrate the effect of adding Ta and Hf, respectively. All exemplary alloys 25 to 35 demonstrated grain sizes less than 30 microns.

Endurance

Figures 26A and 26B show histograms of the yield point elongation test results (Rp02, Figure 26A) and the final tensile test (Rm, Figure 26B). The tests were carried out according to DIN EN ISO 6892-1: 2009, at 90 ° (transverse) in the rolling direction. The increase in Cu from 0.05% by weight to 0.41% by weight showed an improvement in the Rp02 / Rm ratio, shown when alloy 25 is compared with alloy 27. Summary

In some cases, increasing the amount of Si, Mg, Cu and Zn in the exemplary alloys 25 to 33 did not reduce the grain size. However, as seen in alloys 34 and 35, the addition of Ta (alloy 34) and Hf (alloy 35) may slightly increase the grain size in the alloy, but the average grain size is still less than 30 microns. .

Claims (18)

1. An aluminum alloy comprising 0.2 to 0.6 % by weight of Fe, 0.06 to 0.25 % by weight of Mn, up to 0.1% by weight of Si, up to 0.5% in weight of Cu, up to 0.25% by weight of Mg, up to 0.4% by weight of Zn, one or more additional elements selected from the group consisting of Ni up to 0.60% by weight, Ti up to 0, 15% by weight, Co up to 0.60% by weight, Nb up to 0.3% by weight, Cr up to 0.25% by weight, V up to 0.2% by weight, Zr up to 0.25% by weight, Hf up to 0.3% by weight and Ta up to 0.20% by weight and up to 0.15% by weight of impurities, the remainder is Al, where the combined content of Fe, Mn, Cr, Ti, Co, Ni and V present in the alloy ranges from 0.60% by weight to 0.90% by weight. 2. The aluminum alloy of claim 1, comprising 0.25 to 0.55% by weight of Fe, 0.08 to 0.20% by weight of Mn, up to 0.1% by weight of Si, up to 0.25% by weight of Cu, up to 0.25% by weight of Mg, up to 0.20% by weight of Zn, one or more additional elements selected from the group consisting of Ni up to 0.60% by weight , Ti up to 0.15% by weight, Co up to 0.60% by weight, Nb up to 0.3% by weight, Cr up to 0.25% by weight, V up to 0.2% by weight, Zr up to 0, 25% by weight, Hf up to 0.30% by weight and Ta up to 0.20% by weight and up to 0.15% by weight of impurities, the rest is Al. 3. The aluminum alloy of claim 1 or 2, wherein the one or more additional elements comprise Ti in an amount of 0.01 to 0.15% by weight. 4. The aluminum alloy of claim 1 or 2, wherein the one or more additional elements comprise V in an amount of between 0.01 and 0.2% by weight. The aluminum alloy of claim 1 or 2, wherein the one or more additional elements comprise Ni in an amount of between 0.01 and 0.60% by weight. 6. The aluminum alloy of claim 1 or 2, wherein the one or more additional elements comprise Co in an amount of between 0.01 and 0.60% by weight. 7. The aluminum alloy of claim 1 or 2, wherein the one or more additional elements comprise Nb in an amount of between 0.01 and 0.3% by weight. 8. The aluminum alloy of claim 1 or 2, wherein the one or more additional elements comprise Cr in an amount of between 0.01 and 0.2% by weight. The aluminum alloy of claim 1 or 2, wherein the one or more additional elements comprise Zr in an amount of between 0.01 and 0.25% by weight. 10. The aluminum alloy of claim 1 or 2, wherein the one or more additional elements comprise Hf in an amount of between 0.01 and 0.30% by weight. 11. The aluminum alloy of claim 1 or 2, wherein the one or more additional elements comprise Ta in an amount of between 0.01 and 0.20% by weight. 12. The aluminum alloy of claim 1, comprising 0.2 to 0.5% by weight of Fe, up to 0.1% by weight of Si, up to 0.25% by weight of Cu, 0, 1 to 0.2% by weight of Mn, up to 0.1% by weight of Mg, up to 0.15% by weight of Cr, up to 0.20% by weight of Zn, up to 0.60% by weight of Ni , up to 0.12% by weight of Ti, up to 0.60% by weight of Co, up to 0.2% by weight of Nb, up to 0.18% by weight of V, up to 0.25% by weight of Zr , up to 0.30% by weight of Hf, up to 0.15% by weight of Ta and up to 0.15% by weight of impurities, the remainder is Al. 13. The aluminum alloy of any of claims 1-12, wherein the alloy forms a sheet having a grain size of between 10 microns and 30 microns or where the alloy forms a sheet having a grain size between 15 microns and 25 microns. 14. A multilayer metal sheet comprising a core layer and a first cladding layer comprising the aluminum alloy of any of claims 1-13, wherein the core layer comprises a first side and a second side, and the first coating layer is on the first side or the second side. The multilayer metallic foil of claim 14, wherein the core layer comprises an AA6xxx alloy, an AA2xxx alloy, an AA5xxx alloy, or an AA7xxx alloy. 16. The multilayer metal sheet of claims 14 or 15, further comprising a second cladding layer in the center layer, wherein the second cladding layer comprises the aluminum alloy of any of claims 1-13. 17. The multilayer metal foil of claim 16, wherein the first side of the core layer is adjacent to the first skin layer to form a first interface and the second side of the core layer is adjacent to the second skin layer to form a second interface 18. A product prepared from the multilayer metal sheet of any of claims 14-17, wherein the product is a part of the body of the motor vehicle and, in particular, where the part of the vehicle body Engine is a side panel of the body.